Turbine cooling system and method

Abstract

A turbine blade of a gas turbine engine is disclosed. The blade may comprise a first cooling passage and a second cooling passage, where the second cooling passage may be located adjacent a leading edge of the blade. The blade may further comprise at least one slot formed in a partition disposed between the first and second cooling passages, and at least one turbulator disposed within the second passage and downstream the at least one slot.

What is claimed is: 
     
         1 . A turbine blade of a gas turbine engine, the blade comprising:
 a first cooling passage;   a second cooling passage, the second cooling passage being located adjacent a leading edge of the blade;   at least one slot formed in a partition disposed between the first and second cooling passages; and   at least one turbulator disposed within the second passage and downstream of the at least one slot.   
     
     
         2 . The turbine blade of  claim 1 , wherein the at least one turbulator comprises a single strip radially disposed within the second cooling passage. 
     
     
         3 . The turbine blade of  claim 1 , wherein the at least one turbulator includes a plurality of turbulator elements disposed within the second cooling passage. 
     
     
         4 . The turbine blade of  claim 1 , wherein the at least one turbulator is disposed directly downstream of the at least one slot. 
     
     
         5 . The turbine blade of  claim 1 , wherein the at least one slot comprises a plurality of slots, and wherein the at least one turbulator is disposed downstream of each of the plurality of slots. 
     
     
         6 . The turbine blade of  claim 1 , wherein the at least one turbulator is connected to a peripheral wall of the turbine blade within the second cooling passage. 
     
     
         7 . The turbine blade of  claim 1 , wherein a height of the at least one slot is greater than a height of the at least one turbulator. 
     
     
         8 . The turbine blade of  claim 1 , wherein a height of the at least one slot is about two times greater than a height of the at least one turbulator. 
     
     
         9 . The turbine blade of  claim 1 , wherein a distance from an inlet opening of the at least one slot to the at least one turbulator is less than about four times a height of the at least one slot. 
     
     
         10 . The turbine blade of  claim 1 , wherein the at least one turbulator comprises a concave dimple formed in a peripheral wall of the turbine blade. 
     
     
         11 . A system for cooling a turbine blade of a gas turbine engine, the system comprising:
 a first cooling path disposed in an interior of the turbine blade and configured to receive a flow of cooling fluid;   a second cooling path disposed in the interior of the turbine blade and configured to receive the flow of cooling fluid;   a plurality of passages forming each of the first and second cooling paths;   a plurality of slots formed in a partition disposed between two of the plurality of passages forming the first cooling path, wherein the plurality of slots are configured to guide the flow of cooling fluid through the first cooling path; and   at least one turbulator disposed downstream of the flow of cooling fluid flowing through the plurality of slots.   
     
     
         12 . The system of  claim 11 , wherein the at least one turbulator comprises a single strip radially disposed within one of the plurality of passages forming the first cooling path. 
     
     
         13 . The system of  claim 12 , wherein the at least one turbulator is disposed directly downstream of the flow of cooling fluid flowing through the plurality of slots. 
     
     
         14 . The system of  claim 13 , wherein the at least one turbulator is disposed downstream of each of the plurality of slots. 
     
     
         15 . The system of  claim 11 , wherein the at least one turbulator is connected to a peripheral wall of the turbine blade within one of the plurality of passages forming the first cooling path and located adjacent a leading edge of the turbine blade. 
     
     
         16 . The system of  claim 11 , wherein a height of each of the plurality of slots is greater than a height of the at least one turbulator. 
     
     
         17 . The system of  claim 11 , wherein a distance from an inlet opening of each of the plurality of slots to the at least one turbulator is less than about four times a height of each of the plurality of slots. 
     
     
         18 . A method of cooling a turbine blade of a gas turbine engine, the method comprising:
 flowing a cooling fluid through a plurality of passages and through at least one slot formed in a partition disposed between two of the plurality of passages; and   adding turbulence to at least part of the flow of cooling fluid downstream of the at least one slot, the turbulence being adjacent a leading edge of the turbine blade.   
     
     
         19 . The method of  claim 18 , wherein turbulence is added to the flow of cooling fluid directly downstream of the at least one slot. 
     
     
         20 . The method of  claim 18 , further comprising adding turbulence to the entire flow of cooling fluid flowing through the at least one slot.